NASA/TP—2013–217498

Analysis of International Space Station 

Vehicle Materials Exposed on Materials

International Space Station Experiment

From 2001 to 2011

M.M. Finckenor

Marshall Space Flight Center, Huntsville, Alabama

J.L. Golden and M. Kravchenko

The Boeing Company, Houston, Texas

December 2013
	




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i

NASA/TP—2013–217498

Analysis of International Space Station 

Vehicle Materials Exposed on Materials 

International Space Station Experiment

From 2001 to 2011

M.M. Finckenor

Marshall Space Flight Center, Huntsville, Alabama

J.L. Golden and M. Kravchenko

The Boeing Company, Houston, Texas

December 2013

National Aeronautics and

Space Administration

Marshall Space Flight Center • Huntsville, Alabama 35812
ii

Available from:

NASA STI Information Desk

Mail Stop 148

NASA Langley Research Center

Hampton, VA 23681–2199, USA

757–864–9658

This report is also available in electronic form at

<http://www.sti.nasa.gov>

Acknowledgments

The authors would like to acknowledge the hard work and dedication of the many scientists and engineers who 

have made the Materials on International Space Station Experiment (MISSE) program so successful, especially Bill 

Kinard, Gary Pippin, Michael Stropki, Karen Gibson, Rob Walters, and Phil Jenkins. The authors also wish to thank 

Dr. Julie Robinson, Kevin Window, Rod Jones, Annette Sledd, and Ginger Flores for their support of International 

Space Station research. Thanks to Sandie Gibbs and Emmett Given for their talented photography and to Don Burch 

and Curtis Bahr for laboratory support.

TRADEMARKS

Trade names and trademarks are used in this report for identification only. This usage does not constitute an official 

endorsement, either expressed or implied, by the National Aeronautics and Space Administration.
iii

TABLE OF CONTENTS

1. INTRODUCTION ............................................................................................................. 1

2. ENVIRONMENTAL DEFINITIONS ............................................................................... 2

 2.1 MISSE-1 and MISSE-2 ................................................................................................ 4

 2.2 MISSE-3 and MISSE-4 ................................................................................................ 5

 2.3 MISSE-5 ....................................................................................................................... 6

 2.4 MISSE-6 ....................................................................................................................... 7

 2.5 MISSE-7 ....................................................................................................................... 8

3. CONTAMINATION .......................................................................................................... 9

4. SURFACE TREATMENTS FOR METALS ..................................................................... 10

 4.1 Conversion Coatings ..................................................................................................... 10

 4.2 Chromic Acid Anodized Aluminum ............................................................................. 11

 4.3 Sulfuric Acid Anodized Aluminum ............................................................................... 11

 4.4 Electroless Nickel .......................................................................................................... 15

5. THERMAL CONTROL COATINGS ................................................................................ 16

 5.1 White Potassium Silicate Binder Coatings .................................................................... 16

 5.2 White Silicone Binder Coatings .................................................................................... 19

 5.3 Black Potassium Silicate Binder Coatings ..................................................................... 20

6. MULTILAYER INSULATION MATERIALS ................................................................. 21

 6.1 Beta Cloth .................................................................................................................... 21

 6.2 Hook and Loop Tape Fastener ..................................................................................... 23

 6.3 Thread .......................................................................................................................... 24

7. POLYMERS ....................................................................................................................... 26

8. OPTICAL MATERIALS .................................................................................................... 29

9. PART MARKING .............................................................................................................. 32

 9.1 Metalphoto®/Photofoil Labels ..................................................................................... 32

 9.2 Ink Stamp Labels .......................................................................................................... 33

10. DISCUSSION AND CONCLUSIONS ............................................................................. 34

REFERENCES ....................................................................................................................... 35
iv

LIST OF FIGURES

 1. Locations of MISSE-1 through MISSE-4 and MISSE-6 through 

 MISSE-8 on the ISS .................................................................................................. 3

 2. MISSE-1 and MISSE-2 on the Quest Airlock. Photograph taken 

 during the STS-108 mission ....................................................................................... 5

 3. MISSE-5 on P6 truss; nadir side visible ..................................................................... 6

 4. MISSE-6A (left) and MISSE-6B (right) attached to the Columbus module .............. 7

 5. MISSE-7A (left) and MISSE-7B (right) on ELC-2 .................................................... 8

 6. ESCA of gold mirror from MISSE-2 wake side ........................................................ 9

 7. SAA aluminum frame, probably with NiAc seal. Lighter circles are where 

 washers shielded the aluminum from UV radiation and are the original 

 color of the frame ..................................................................................................... 12

 8. MISSE-7B wake baseplate after most of the samples had been removed, 

 showing UV darkening where the aluminum was exposed ......................................... 14

 9. Postflight MISSE-2 dyed anodize samples ................................................................. 15

10. Aplix tape fastener samples from MISSE-2 ram side, showing UV darkening 

 and nubs: (a) Hook and (b) loop .............................................................................. 23

11. Triton TOR cloth and thread, MISSE-1 ram. Octagon is where sample 

 was exposed to space ................................................................................................. 24

12. Samples of beta cloth sewn with reinforced thread .................................................... 25

13. Comparison of MISSE versus POSA for vacuum UV transmission

 of magnesium fluoride .............................................................................................. 29

14. Transmission of Russian quartz samples flown on MISSE-6B .................................. 30

15. Hyzod polycarbonate flown on MISSE-6B wake side ................................................ 30

16. Visible wavelength transmission for Hyzod polycarbonate ........................................ 31
v

LIST OF FIGURES (Continued)

17. ISS S1 truss with (A) NiAc-sealed labels, which darkened, and (B) nickel-free 

 labels, which were stable ............................................................................................ 32

18. Metalphoto/Photofoil from MISSE-1 wake-facing side. White circles 

 are where washers protected the surface from UV radiation ...................................... 33

19. Ink stamp with clear overcoat from MISSE-1 ram-facing side .................................. 33
vi

LIST OF TABLES 

 1. Mission exposure summary of MISSE-1 through MISSE-8 ...................................... 2

 2. MISSE-1 and MISSE-2 environments ....................................................................... 5

 3. MISSE-3 and MISSE-4 environments ....................................................................... 5

 4. MISSE-6A and MISSE-6B environments .................................................................. 7

 5. MISSE-7B environment ............................................................................................ 8

 6. Optical properties of MISSE conversion coatings ..................................................... 10

 7. Optical properties for SAA aluminum samples ......................................................... 12

 8. Optical properties for SAA aluminum hardware ....................................................... 13

 9. Optical properties for black dyed anodized aluminum ............................................... 15

10. Optical properties for electroless nickel ..................................................................... 15

11. Optical properties for Alion Science zinc oxide/potassium silicate coating ................ 16

12. Optical properties for AZ Technology zinc oxide/potassium silicate coating ............. 17

13. Optical properties for Alion Science zinc orthotitanate/potassium silicate coating .... 18

14. Optical properties for AZ Technology zinc orthotitanate/potassium

 silicate coating ........................................................................................................... 18

15. Optical properties for Alion Science zinc oxide/silicone binder coating ..................... 19

16. Optical properties for AZ Technology zinc oxide/silicone binder coating .................. 19

17. Optical properties for aluminized beta cloth .............................................................. 22

18. Optical properties for plain beta cloth ....................................................................... 22

19. Optical properties for super or plus beta cloth ........................................................... 23
vii

LIST OF TABLES (Continued)

20. Optical properties for PFOA-free beta cloth, black background ............................... 23

21. Optical properties for aluminized Teflon ................................................................... 26

22. Optical properties for silverized Teflon ...................................................................... 27

23. Optical properties for silverized Teflon with SiOx coating .......................................... 27

24. Optical properties for ITO on Kapton ....................................................................... 28
viii

LIST OF ACRONYMS AND SYMBOLS

AO atomic oxygen

CAA chromic acid anodized

DI deionized

ELC EXPRESS Logistics Carrier

ESCA electron spectroscopy for chemical analysis

ESH equivalent sun hour(s)

EXPRESS EXpedite the PRocessing of Experiments to Space Station

HPGT high-pressure gas tank

ISS International Space Station

ITO indium tin oxide

LDEF Long Duration Exposure Facility

MISSE Materials on International Space Station Experiment

MLI multilayer insulation

MSFC Marshall Space Flight Center

NASA National Aeronautics and Space Administration

NiAc nickel acetate

O oxygen

ORMatE R/W Optical Reflector Materials Experiment ram/wake

PEC passive experiment container

PFOA perfluorooctanoic acid

POSA Passive Optical Sample Assembly

PTFE polytetrafluoroethylene

SAA sulfuric acid anodize

SiOx silicon oxide

STS Space Transportation System

TOR Triton oxygen resistant

TP Technical Publication

UV ultraviolet
ix

NOMENCLATURE

α absorptance

αs solar absorptance

ε emittance, thermal emittance
x
1

TECHNICAL PUBLICATION

ANALYSIS OF INTERNATIONAL SPACE STATION VEHICLE MATERIALS 

EXPOSED ON MATERIALS INTERNATIONAL SPACE STATION 

EXPERIMENT FROM 2001 TO 2011

1. INTRODUCTION

 Since August 2001, the Materials on International Space Station Experiment (MISSE) has 

provided a wealth of space environmental effects data on a variety of materials and spacecraft components. Many of these materials samples were chosen to provide engineering data for the International Space Station (ISS) vehicle itself. These data are vital for mission planning and life extension 

of the ISS. This Technical Publication (TP) is a compilation of several conference presentations1–14

and previously unpublished data. This is by no means a complete set of MISSE data, but the authors 

have attempted to include the most pertinent from MISSE-1 through MISSE-7 for materials and 

processes engineers. MISSE-8 is on orbit, so analyses of these samples have not yet been performed. 

MISSE-8 is scheduled for return in 2014. 

 Reference 15 is a good source of information on MISSE polymer materials not covered in 

this TP. The National Aeronautics and Space Administration (NASA) gives no recommendation, 

endorsement, or preference, either expressed or implied, concerning materials and vendors used.

 Unless otherwise specified, solar absorptance (αs) measurements were made with an AZ Technology Laboratory Portable Spectroreflectometer model 300. Infrared emittance (ε) measurements 

were made with an AZ Technology TEMP 2000A infrared reflectometer. Changes of ±0.01 in these 

optical properties are not considered statistically significant.
2

2. ENVIRONMENTAL DEFINITIONS

 MISSE is a series of materials flight experiments, the first two of which were delivered to 

the ISS during Space Transportation System-105 (STS-105) in 2001. Experiments developed by 

principal investigators were loaded onto hinged, suitcase-like containers, called passive experiment 

containers (PECs), and were exposed to the space environment on the exterior of the ISS. During 

transport to the ISS on the Space Shuttle, the PECs were closed with the samples facing each other 

for protection; once the Space Shuttle reached the ISS, the PECs were attached to its exterior during 

an extravehicular activity and opened back-to-back, exposing the samples to space. In the MISSE 

suite (MISSE-1 through MISSE-8), 10 PECs and one smaller tray, together containing thousands of 

samples, have been flown in various external locations on the ISS. (See table 1.) Figure 1 shows the 

ISS locations of MISSE-1 through MISSE-8. Note that the earlier MISSE flights were numbered for 

each PEC, so that MISSE-1 and MISSE-2 flew together, as did MISSE-3 and MISSE-4. The later 

flights were single numbers with different letters for each PEC, e.g., MISSE-6A and MISSE-6B.

Table 1. Mission exposure summary of MISSE-1 through MISSE-8.

MISSE

Launch

Mission

Placed

Outside ISS

Location 

on ISS

Tray

Orientation

Retrieval 

Mission

Retrieved

From ISS

Exposure

(yr)

1, 2 STS-105 8/16/01 MISSE 1: High-pressure gas tank (HPGT) 

MISSE 2: Quest Airlock 

Ram and wake STS-114 7/30/05 3.95

3, 4 STS-121 8/3/06* MISSE 3: HPGT 

MISSE 4: Quest Airlock

Ram and wake STS-118 8/18/07 1.04

5 STS-114 8/3/05 Aft P6 trunion pin 

handrail

Zenith and nadir STS-115 9/15/06 1.12

6A, 6B STS-123 3/22/08 Columbus Laboratory Ram and wake STS-128 9/1/09 1.45

7A, 7B STS-129 11/23/09 EXPRESS Logistics 

Carrier 2 (ELC 2) on 

the S3 Truss

7A: Zenith and 

nadir

7B: Ram and wake 

STS-134 5/20/11 1.49

8 and ORMatE 

-III R/W

STS-134 8: 5/20/11;

ORMatE-III 

R/W: 7/12/11**

ELC 2 on the 

S3 Truss

8: Zenith and nadir; 

ORMatE-III R/W: 

ram and wake

Manifested on 

SpaceX Dragon

Retrieved 7/9/13 

and stored in ISS

On orbit

 *Deployed during Expedition 13

**Deployed during STS-135
3

Quest Airlock

Columbus EPF

MISSE-6

ELC (starboard)

MISSE-7

MISSE-8

MISSE-1

MISSE-2

MISSE-3

MISSE-4

Figure 1. Locations of MISSE-1 through MISSE-4 and MISSE-6 through MISSE-8 

on the ISS.

With participants from NASA, the Department of Defense, industry, and academia, MISSE 

is the longest running multiorganization technology, development, and materials testing project on 

the ISS. It has provided many tangible benefits for the Agency and its partners, with the flight data 

impacting many space programs. MISSE flight data have provided a great wealth of space performance and environmental durability data and enable lifetime prediction of new materials and components that may be used in future spaceflight. Published MISSE data, photographs, and some raw 

data files are being gathered in a database in the Materials and Processes Technical Information 

System.

 

The MISSE PECs are flown in either a ram/wake orientation, i.e., leading edge/trailing edge 

facing, or a zenith/nadir orientation, i.e., space facing/Earth facing. Each of these orientations provides different space environmental exposures. For example, samples in a ram orientation receive 

the greatest amount of atomic oxygen (AO) exposure combined with solar radiation exposure, while 

those in a wake orientation receive solar radiation exposure with very little AO exposure. Zenithfacing samples receive the highest amount of solar radiation and grazing AO exposure, and nadirfacing samples receive little solar exposure (only ambient reflected solar exposure) with grazing AO 

exposure. 
4

 The design of the MISSE suitcases allows for materials on one side to receive either a higher 

fluence of AO or higher incident ultraviolet (UV) radiation. MISSE-5 and MISSE-7A were positioned so that one side of each faced in the zenith direction for the most sunlight, and the other side 

faced in the nadir direction. All other MISSE experiments discussed in this TP were ram-/wakefacing. While the ram-facing side was intended to receive the most AO, this does not mean that the 

wake side did not receive any AO. The ISS has many orientations, including one during which the 

MISSE experiment wake side faced the ram direction. In general, the wake side samples received an 

order of magnitude less AO than the ram side samples. This means that, while material darkening 

related to UV radiation is sometimes more obvious on the wake side samples, these samples still 

experience AO erosion or bleaching. 

 MISSE samples were exposed just past the solar cycle maximum and through the solar minimum. Thus, samples exposed on MISSE-7 were exposed to twice as much AO as those samples on 

MISSE-6, even though MISSE-6 was exposed for 1 month less than MISSE-7. 

 The reader should not assume that, because one material survived for a year on orbit, it 

would survive a year in any orbit, any environment, any orientation, at any point in the solar cycle. 

It is critical to model the expected use environment and choose materials accordingly.

 The environmental data are presented in numerical order rather than chronological order, 

as MISSE-5 was flown before MISSE-3 and MISSE-4. For simplicity, only AO and UV environment definitions are given. Details of these environments may be found in references 16–19. (Material effects related to particulate radiation or micrometeoroid/space debris impacts on MISSE were 

negligible.) 

2.1 MISSE-1 and MISSE-2

 MISSE-1 and MISSE-2 were deployed in August 2001 during STS-104 and retrieved in July 

2005 during STS-114. They were attached to the Quest Airlock (fig. 2). The intended duration was 

1 year, but retrieval was delayed because of the Space Shuttle Columbia accident. Table 2 presents 

their environments in terms of AO fluence (given as oxygen atoms/cm2) and UV radiation in equivalent sun hours (ESH).
5

MISSE-1

MISSE-2

Figure 2. MISSE-1 and MISSE-2 on the Quest Airlock. Photograph 

taken during the STS-108 mission. 

Table 2. MISSE-1 and MISSE-2 environments. 

AO Fluence

(atoms/cm2)

UV Radiation

(ESH)

MISSE-1 ram-facing side 9 × 1021 (est.) 5,400 – 6,400

MISSE-1 wake-facing side 1.1 – 1.3 × 1020 4,500 – 5,600

MISSE-2 ram-facing side 8 – 9 × 1021 5,000 – 6,700

MISSE-2 wake-facing side 1.7 – 2 × 1020 4,800 – 6,200

2.2 MISSE-3 and MISSE-4

 MISSE-3 and MISSE-4 were deployed in August 2006 during STS-121 and retrieved in August 

2007 during STS-118. They were attached to the Quest Airlock in the same locations as MISSE-1 

and MISSE-2. Table 3 presents their environments.

Table 3. MISSE-3 and MISSE-4 environments.

AO Fluence

(atoms/cm2)

UV Radiation

(ESH)

MISSE-3 ram-facing side 1.2 – 1.3 × 1021 1,750

MISSE-3 wake-facing side 1.9 × 1020 790

MISSE-4 ram-facing side 2.1 × 1021 1,590

MISSE-4 wake-facing side 3.6 × 1020 (est.) 995
6

2.3 MISSE-5

 MISSE-5 was deployed in July 2005 during STS-114 and retrieved in July 2006 during STS115. It was attached to the P6 truss (fig. 3), when P6 was mounted on the Z1 truss. Solar cells made 

up the zenith-facing side, while a blanket of materials samples covered the nadir side. The AO fluence 

for the nadir-facing side was 1.8 × 1020 atoms/cm2, and the estimated UV exposure was 160 ESH.

Figure 3. MISSE-5 on P6 truss; nadir side visible. 
7

2.4 MISSE-6

 MISSE-6A and MISSE-6B were deployed in March 2008 during STS-123 and retrieved in 

September 2009 during STS-128. They were attached to the Columbus module (fig. 4). Table 4 presents their environments.

Figure 4. MISSE-6A (left) and MISSE-6B (right) attached to the Columbus module.

Table 4. MISSE-6A and MISSE-6B environments. 

AO Fluence

(atoms/cm2)

UV Radiation

(ESH)

MISSE-6A ram-facing side 2 × 1021 2,600

MISSE-6A wake-facing side 1.4 × 1020 1,950

MISSE-6B ram-facing side 2 × 1021 2,600

MISSE-6B wake-facing side 1.2 × 1020 1,950
8

2.5 MISSE-7

 MISSE-7A and MISSE-7B were deployed in November 2009 during STS-129 and retrieved 

in May 2011 during STS-134. They were attached to the EXpedite the PRocessing of Experiments to 

Space Station (EXPRESS) Logistics Carrier 2 (ELC-2) (fig. 5). Table 5 presents environmental data 

for MISSE-7B. Similar data for MISSE-7A, which was a zenith-/nadir-facing experiment, were not 

available at time of publication.

Figure 5. MISSE-7A (left) and MISSE-7B (right) on ELC-2. 

Table 5. MISSE-7B environment. 

AO Fluence

(atoms/cm2)

UV Radiation

(ESH)

MISSE-7B ram-facing side 4.2 × 1021 2,400

MISSE-7B wake-facing side 2.9 × 1020 2,000
9

3. CONTAMINATION

 Molecular contamination can skew the results of a space environmental effects investigation. 

Several optical witness samples were flown on each MISSE experiment to monitor contamination 

and to indicate how well the ISS contamination control plan was working. When possible, electron 

spectroscopy for chemical analysis (ESCA) and ellipsometry were performed on these optical witness samples to determine contaminant buildup.

 There have been instances of localized contamination on the MISSE experiments, but overall, 

they have been fairly clean, on the order of 500 Å of silicate or less. This amount is enough to affect 

sensitive optics but not enough to impact radiator performance. Figure 6 shows the worst case of 

contamination observed by ESCA, which was a gold optical witness sample flown on the wake side 

of MISSE-2 for nearly 4 years. A similar gold mirror flown on the ram side of MISSE-2 only had 

50 Å of silicate. This measurement was in good agreement with ellipsometry results.

100

90

80

70

60

50

40

30

20

10

0

Atomic Percent

Angstrom Sputtered

0 100 200 300 400 500 600 700 800 900 1,000

Carbon

Oxygen

Silicon

Gold

Figure 6. ESCA of gold mirror from MISSE-2 wake side. 
10

4. SURFACE TREATMENTS FOR METALS

 This section covers chemical conversion coatings in accordance with MIL-DTL-5541F, 

Military Specification: Chemical Conversion Coatings on Aluminum and Aluminum Alloys,20 and 

anodic coatings in accordance with MIL-A-8625, Military Specification: Anodic Coatings for Aluminum and Aluminum Alloys,21 for aluminum. These coatings are mainly for corrosion protection, 

but much of the ISS anodized aluminum structure was tailored for a specific range of αs and ε for 

passive thermal control.

 In this section, Anadite, George, and Mooney refer to the specific vendors contracted for surface treatments: Anadite, Inc.; George Industries; and Mooney Anodize. Samples labeled Boeing or 

Marshall Space Flight Center (MSFC) were processed by the respective in-house fabrication shops.

4.1 Conversion Coatings

 All of the conversion coatings on 2219 aluminum were flown on the MISSE-3 ram and wake 

sides. The iridite on 2195 aluminum-lithium alloy was flown on the MISSE-6B wake side. Table 6 lists 

the optical properties of the MISSE conversion coatings.

Table 6. Optical properties of MISSE conversion coatings.

	 		  Environment

Anadite chromate 

on 2219-T851

MISSE-3 ram

0.50 0.51 0.01 1,750 ESH 

 0.07 0.07 – 1.2 × 1021 O atoms/cm2

Anadite chromate

on 2219-T851

MISSE-3 wake

0.49 0.49 – 790 ESH 

 0.07 0.07 – 1.9 × 1020 O atoms/cm2

George chromate

on 2219-T851

MISSE-3 ram

0.35 0.40 0.05 1,750 ESH 

 0.05 0.06 0.01 1.2 × 1021 O atoms/cm2

George chromate

on 2219-T851

MISSE-3 wake

0.35 0.42 0.07 790 ESH 

 0.07 0.07 – 1.9 × 1020 O atoms/cm2

Boeing chromate

on 2219-T851

MISSE-3 ram

0.47 0.48 0.01 1,750 ESH 

 0.05 0.06 0.01 1.2 × 1021 O atoms/cm2

MSFC 12-4 iridite

on 2195

MISSE-6 wake

0.31 0.31 – 1,950 ESH

 0.05 0.04 –0.01 1.2 × 1020 O atoms/cm2
11

4.2 Chromic Acid Anodized Aluminum

 As previously mentioned, most of the ISS structure and meteoroid/debris shields are chromic acid anodized (CAA) aluminum. While there is a wealth of CAA data from the Long Duration 

Exposure Facility (LDEF)22 there are only a few data points for MISSE, and these are mainly for 

comparison to other anodize types. CAA aluminum (6061-T6), flown on the wake side of MISSE-6, 

had a slight increase in αs from 0.32 to 0.34 and a slight decrease in ε from 0.49 to 0.46. Several of 

the older sample trays are CAA aluminum. While preflight data for these trays were not available, 

postflight measurements were 0.28 to 0.31 for αs and 0.66 to 0.67 for ε.

4.3 Sulfuric Acid Anodized Aluminum

 Sulfuric acid anodize (SAA) became more widely used as the Environmental Protection 

Agency restricted the use of chromium. This restriction also led to the elimination of sodium chromate, used to seal SAA. MIL-A-8625, Type II, calls for sodium chromate, nickel acetate (NiAc), 

cobalt acetate, or hot water seal. Cobalt acetate seal has not been flown on MISSE. Data from the 

earlier Passive Optical Sample Assembly-I (POSA-I) experiment indicated that anodized aluminum 

treated with either NiAc or nickel fluoride would darken after only 800 ESH of UV radiation.23 The 

authors recommend hot deionized (DI) water seal for MIL-A-8625, Type II anodize. 

 Table 7 contains the optical property data for a variety of MISSE SAA aluminum samples. 

These do not include the SAA with preflight contamination, which are discussed in reference 8. 

Measurements made directly on sample trays, frames (example shown in fig. 7), and baseplates are 

included in table 8.
12

Table 7. Optical properties for SAA aluminum samples.

	 		  Environment

SAA on 2219-T851, 

DI seal

MISSE-2 ram

0.47 0.48 0.01 6,600 ESH

 0.86 0.88 0.02 9 × 1021 O atoms/cm2

Anadite SAA 

on 2219-T851 

MISSE-3 ram

0.41 0.42 0.01 1,750 ESH 

 0.89 0.88 –0.01 1.2 × 1021 O atoms/cm2

Anadite SAA 

on 2219-T851 

MISSE-3 wake

0.46 0.48 0.02 790 ESH 

 0.89 0.88 –0.01 1.9 × 1020 O atoms/cm2

George SAA 

on 2219-T851 

MISSE-3 ram

0.42 0.48 0.06 1,750 ESH 

 0.90 0.88 –0.02 1.2 × 1021 O atoms/cm2

George SAA 

on 2219-T851 

MISSE-3 wake

0.41 0.47 0.06 790 ESH 

 0.90 0.87 –0.03 1.9 × 1020 O atoms/cm2

Boeing SAA 

on 2219-T851 

MISSE-3 ram

0.44 0.49 0.05 1,750 ESH 

 0.88 0.85 –0.03 1.2 × 1021 O atoms/cm2

Boeing SAA 

on 2219-T851 

MISSE-3 wake

0.40 0.46 0.06 790 ESH 

 0.87 0.84 –0.03 1.9 × 1020 O atoms/cm2

George SAA 

on 7075-T3751 

MISSE-3 ram

0.44 0.49 0.05 1,750 ESH 

 0.87 0.87 – 1.2 × 1021 O atoms/cm2

 

Figure 7. SAA aluminum frame, probably with NiAc seal. Lighter circles are where washers 

shielded the aluminum from UV radiation and are the original color of the frame. 
13

Table 8. Optical properties for SAA aluminum hardware.

Unexposed Exposed  Environment

N1 frame

NiAc seal,

MISSE-2 wake

0.46 0.56 0.10 5,700 ESH

 0.83 0.83 – 1 × 1020 O atoms/cm2

N2 frame

NiAc seal,

MISSE-2 wake

0.49 0.57 0.08 5,700 ESH

 0.84 0.83 –0.01 1 × 1020 O atoms/cm2

N3 frame

NiAc seal,

MISSE-1 wake

0.49 0.59 0.10 5,400 ESH

 0.84 0.84 – 1.2 × 1020 O atoms/cm2

N4 frame

NiAc seal,

MISSE-1 wake

0.46 0.57 0.11 5,400 ESH

 0.83 0.83 – 1.2 × 1020 O atoms/cm2

Sample tray

hot DI water,

MISSE-6 ram

0.44 0.43 –0.01 2,600 ESH

 0.85 0.85 – 2 × 1021 O atoms/cm2

Sample tray

hot DI water,

MISSE-6 wake

0.43 0.43 – 1,950 ESH

 0.85 0.85 – 1.2 × 1020 O atoms/cm2

Unknown seal

baseplate, 

MISSE-7B ram

0.49 0.52 0.03 2,400 ESH

 0.87 0.87 – 4.2 × 1021 O atoms/cm2

Unknown seal

baseplate, 

MISSE-7B wake

0.49 0.53 0.04 2,000 ESH

 0.87 0.87 – 2.9 × 1020 O atoms/cm2
14

 The anodize instructions for the MISSE-7B baseplate specified hot DI water seal, but the 

baseplate visibly darkened (fig. 8). Different batches of SAA from the same plating shop for MISSE7B did not darken. Chemical analysis has not yet been performed to determine the presence of 

nickel.

Figure 8. MISSE-7B wake baseplate after most of the samples had been 

removed, showing UV darkening where the aluminum was exposed. 

 Several class 2, or dyed anodize, samples have been flown on MISSE. Optical property data 

are presented only for the black dyed anodize. Concerns regarding gold, blue, and red anodize center 

on color maintenance, not on optical properties. Yellow anodize is used to indicate areas that can 

hold an astronaut, such as handrails and tether points. Red anodize is used to indicate no-touch 

zones, such as areas of hypergolic residue from engine ports or where high temperatures may damage the astronaut’s gloves. Early tests of dyed anodize during the Space Station Freedom program 

caused some concern, where yellow and red anodizes changed in simulated space environments to 

nearly the same shade of brown. Previous space environment testing of dyed anodize is discussed in 

reference 24. The Aacron, Inc., dyed anodize samples flown on MISSE-2 maintained their color with 

6,600 ESH of UV and 8 × 1021 atoms/cm2 of AO (fig. 9).
15

2-E8-15 2-E8-17 2-E8-18

Figure 9. Postflight MISSE-2 dyed anodize samples. 

 It should be noted that attempts at MSFC to black dye anodize aluminum-lithium alloy, 

specifically AL 2195, have been unsuccessful to date. The black dye particles can be wiped off after 

processing. Table 9 lists optical properties for black dyed anodized aluminum.

 Table 9. Optical properties for black dyed anodized aluminum.

	 		  Environment

7075 clad 

with 7072 

MISSE-2 AaCron

 0.90 0.90 – 6,600 ESH

 0.85 0.85 – 8 × 1021 O atoms/cm2

6061-T6x

MISSE-7B ram

Mooney anodize

 0.71 0.70 –0.01 2,400 ESH 

 0.86 0.87 0.01 4.2 × 1021 O atoms/cm2

6061-T6x 

MISSE-7B wake 

Mooney anodize

 0.69 0.68 –0.01 2,000 ESH 

 0.86 0.86 – 2.9 × 1020 O atoms/cm2

4.4 Electroless Nickel

 Electroless nickel is used on fluid and electrical connectors. It is usually covered with multilayer insulation (MLI) for thermal control, but there was enough concern for possible exposure of 

electroless-nickel-plated parts to include samples on MISSE-6. These samples were processed by AZ 

Technology of Huntsville, AL. This coating appeared to be stable in a low Earth orbital environment 

(table 10).

Table 10. Optical properties for electroless nickel. 

	 		  Environment

MISSE-6 ram 0.42 0.41 –0.01 2,600 ESH

 0.09 0.09 – 2 × 1021 O atoms/cm2

MISSE-6 wake 0.39 0.39 – 1,950 ESH

 0.09 0.09 – 1.2 × 1020 O atoms/cm2
16

5. THERMAL CONTROL COATINGS

 Whether as part of an active thermal control system or simple passive thermal control, coatings such as Z-93 must maintain their optical properties and mechanical integrity.

5.1 White Potassium Silicate Binder Coatings

 Passive thermal control coatings with potassium silicate binder have shown good durability 

in the space environment, provided they are properly applied and kept free of contamination. Zinc 

oxide pigment in a potassium silicate binder, sold as Z-93 by Alion Science and Technology Corporation (formerly known as IITRI) or AZ93 by AZ Technology, has been flown on every MISSE 

experiment. (Tables 11 and 12 list optical properties for these two companies’ products, respectively.) 

Z-93 and Z-93P have been used interchangeably in other documents. The original Z-93 used PS7 

potassium silicate binder, which was discontinued in the early 1990s. Coatings made with the replacement Kasil 2135 potassium silicate binder are designated Z-93P. Kasil 2130 has also been approved 

as a replacement binder. The reader should be aware of these differences when comparing data from 

before 1991 to MISSE data. 

Table 11. Optical properties for Alion Science zinc oxide/potassium silicate coating.

	




Control 		  Environment

Z-93P on

aluminum,

MISSE-2 ram

0.14 0.13 –0.01 6,000 ESH

 0.91 0.90 –0.01 7.6 × 1021 O atoms/cm2

Z-93P on

aluminum,

MISSE-2 wake

0.14 0.14 – 4,900 ESH

 0.91 0.91 – 1.4 × 1020 O atoms/cm2

Z-93P on

aluminum,

MISSE-3 ram

0.14 0.15 0.01 1,750 ESH 

 0.91 0.91 – 1.2 × 1021 O atoms/cm2

Z-93P on

aluminum,

MISSE-4 wake

0.14 0.14 – 900 ESH 

 0.91 0.91 – 3.6 × 1020 O atoms/cm2

Z-93P on

aluminum,

MISSE-6 ram

0.14 0.14 – 2,600 ESH

 0.91 0.91 – 2 × 1021 O atoms/cm2
17

Table 12. Optical properties for AZ Technology zinc oxide/potassium silicate coating. 

	




Control 		  Environment

AZ93 on

6061-T651(Boeing),

MISSE-1 ram

0.16 0.15 –0.01 7,000 ESH

 0.93 0.91 –0.02 9 × 1021 O atoms/cm2

AZ93 on

6061-T6x (MSFC),

MISSE-2 ram

0.15 0.15 – 6,000 ESH

 0.92 0.92 – 7.6 × 1021 O atoms/cm2

AZ93 on

6061-T6x,

MISSE-3 ram

0.15 0.15 – 1,750 ESH

 0.91 0.91 - 1.2 × 1021 O atoms/cm2

AZ93 on

6061-T6x,

MISSE-3 wake

0.15 0.16 0.01 790 ESH

 0.91 0.91 – 1.9 × 1020 O atoms/cm2

AZ93 on

6061-T6x,

MISSE-4 ram

0.15 0.15 – 1,590 ESH

 0.91 0.91 – 2.1 × 1021 O atoms/cm2

AZ93 on

6061-T6x, 

MISSE-6B ram

0.17 0.17 – 2,600 ESH

 0.91 0.91 – 2 × 1021 O atoms/cm2

AZ93 on

6061-T6x,

MISSE-6B wake

0.17 0.17 – 1,950 ESH

 0.91 0.91 – 1.2 × 1020 O atoms/cm2

AZ93 on

6061-T6x, 

MISSE-7B ram

0.16 0.16 – 2,400 ESH

 0.91 0.91 – 4.2 × 1021 O atoms/cm2

AZ93 on

6061-T6x,

MISSE-7B wake

0.16 0.16 – 2,000 ESH

 0.91 0.91 – 2.9 × 1020 O atoms/cm2

AZ93 on

Composite,

MISSE-1 ram

0.15 0.16 0.01 5,700 ESH

 0.91 0.91 – 9 × 1021 O atoms/cm2

AZ93 on

Kapton,

MISSE-5 nadir

0.21 0.22 0.01 525 ESH

 0.92 0.92 – 1.8 × 1020 O atoms/cm2

AZ93 on

Beta cloth,

MISSE-6 ram

0.17 0.17 – 2,600 ESH

 0.92 0.92 – 2 × 1021 O atoms/cm2

AZ93 on

	



MISSE-6 wake

0.18 0.18 – 1,950 ESH

 0.92 0.92 – 1.2 × 1020 O atoms/cm2
18

 Not only is this material used on the Active Thermal Control System radiators, it is a bellwether for effects of contamination. Z-93P exposed on the POSA experiment on Mir increased in 

αs from 0.15 to 0.23 because of 5,000 Å of contamination and only 571 ESH of UV radiation.25

By contrast, the same coating was within instrument error of the original solar absorptance after 

6,000 ESH exposure on MISSE-2.

 Another class of coatings with potassium silicate binder uses zinc orthotitanate for the pigment. Alion Science YB-71P (with P again denoting the use of Kasil 2135 binder instead of the 

original PS7 binder) and AZ Technology AZ-70-WIZT were flown on MISSE-2. Tables 13 and 14 

list the optical properties for these two companies’ products, respectively.

Table 13. Optical properties for Alion Science zinc orthotitanate/potassium 

silicate coating. 

	




Control 		  Environment

YB-71P on

aluminum

MISSE-2 ram

0.12 0.11 –0.01 6,000 ESH

 0.86 0.87 0.01 7.6 × 1021 O atoms/cm2

YB-71P on

aluminum

MISSE-2 wake

0.12 0.12 – 4,900 ESH

 0.86 0.87 0.01 1.4 x 1020 O atoms/cm2

YB-71P on

aluminum

MISSE-3 ram

0.12 0.12 – 1,750 ESH 

 0.87 0.88 0.01 1.2 × 1021 O atoms/cm2

YB-71P on

aluminum

MISSE-4 wake

0.12 0.12 – 900 ESH 

 0.87 0.88 0.01 3.6 × 1020 O atoms/cm2

Table 14. Optical properties for AZ Technology zinc orthotitanate/potassium 

silicate coating. 

	




Control 		  Environment

AZ70-WIZT

on aluminum

MISSE-1 ram

0.09 0.09 – 5,700 ESH 

 0.91 0.90 –0.01 9 × 1021 O atoms/cm2

AZ70-WIZT

on aluminum

MISSE-2 ram

0.10 0.10 – 6,000 ESH

 0.91 0.91 – 7.6 × 1021 O atoms/cm2
19

5.2 White Silicone Binder Coatings

 Thermal control coatings with low outgassing silicone binders are used when the surface is 

difficult to paint or when temperature and humidity cannot be controlled during the coating application. Some of these coatings tend to darken in UV but may still have acceptable end-of-life properties 

for certain missions, especially where AO may bleach the coating. The more commonly used silicone 

binder coatings are Alion Science’s S13G/LO-1 and S13GP:6N/LO-1 and AZ Technology’s AZ400. 

Tables 15 and 16 list the optical properties for these two companies’ products, respectively.

Table 15. Optical properties for Alion Science zinc oxide/silicone binder coating. 

	 		  Environment

S13G/LO-1 

on aluminum,

MISSE-2 ram

0.20 0.20 – 6,000 ESH

 0.89 0.89 – 7.6 × 1021 O atoms/cm2

S13G/LO-1 

on aluminum,

MISSE-2 wake

0.20 0.45 0.25 4,900 ESH

 0.89 0.87 –0.02 1.4 × 1020 O atoms/cm2

S13GP:6N/LO-1 

on aluminum,

MISSE-2 ram

0.18 0.20 0.02 6,000 ESH

 0.90 0.89 –0.01 7.6 × 1021 O atoms/cm2

S13GP:6N/LO-1 

on aluminum,

MISSE-2 wake

0.18 0.34 0.16 4,900 ESH

 0.90 0.90 – 1.4 × 1020 O atoms/cm2

S13GP:6N/LO-1

on aluminum,

MISSE-3 ram

0.18 0.20 0.02 1,750 ESH 

 0.90 0.90 – 1.2 × 1021 O atoms/cm2

S13GP:6N/LO-1 

on aluminum,

MISSE-4 wake

0.18 0.23 0.05 900 ESH 

 0.90 0.89 –0.01 3.6 × 1020 O atoms/cm2

Table 16. Optical properties for AZ Technology zinc oxide/silicone binder coating.

	 		  Environment 

AZ400 conductive

on aluminum,

MISSE-6 ram

0.23 0.23 – 2,600 ESH

 0.92 0.91 –0.01 2 × 1021 O atoms/cm2

AZ400 conductive 

on aluminum,

MISSE-6 wake

0.23 0.23 – 1,950 ESH

 0.92 0.92 – 1.2 × 1020 O atoms/cm2 

AZ400 on aluminum, 

MISSE-7 ram 0.15 0.16 0.01 2,400 ESH 

 0.85 0.86 0.01 4.2 × 1021 O atoms/cm2 

AZ400 on aluminum,

MISSE-7 wake 0.15 0.16 0.01 2,000 ESH 

 0.85 0.85 – 2.9 × 1020 O atoms/cm2
20

5.3 Black Potassium Silicate Binder Coatings

 AZ Technology RM-550 black coating with the inorganic potassium silicate binder has been 

used on the ISS in various places, including the docking targets. Samples flown on MISSE-6 and 

MISSE-7 ram and wake maintained αs of 0.97 and ε of 0.90.
21

6. MULTILAYER INSULATION MATERIALS

 MLI blankets are composed of reflector layers of thin polymer films with metallization on 

one or both sides, usually with netting or another separator layer in between. MLI blankets on the 

ISS are usually 15 to 20 double-aluminized Kapton® reflector layers with outer and inner covers for 

ease of handling and durability in the space environment. 

6.1 Beta Cloth 

 Beta cloth is a woven fiberglass mat impregnated with Teflon®. MLI blankets for ISS 

have usually been Saint-Gobain/Chemfab 500F with aluminization on one side and no polysiloxane. For Space Shuttle MLI blankets, the Chemfab 250F usually had ≈2% polysiloxane added 

for flexibility, but this was a contamination concern and caused the Chemfab 250F to darken 

more in UV.26 Various samples of beta cloth have been flown on every MISSE: aluminized beta 

cloth samples taken from scraps left over from manufacturing the ISS MLI blankets are referred 

to as ‘ISS batch,’ ‘plain’ beta cloth refers to unaluminized beta cloth, and ‘super’ beta cloth and 

beta cloth ‘plus’ refer to a change to slightly larger glass denier in the weave. After the removal 

of perfluorooctanoic acid (PFOA) from the Teflon process in 2007, ‘PFOA-free’ beta cloth was 

manufactured.

 Two samples of black beta cloth were flown on MISSE-5. This form of beta cloth has carbon 

black impregnated in the Teflon. Exposure to AO increased the αs from 0.95 to 0.96 and 0.97, but ε

was unchanged at 0.89.

 It should be noted that beta cloth is slightly transmissive; therefore, the background used on 

the sample will affect the αs measurement. Unless otherwise noted, a blackbody background was 

used for the optical property measurements listed in tables 17–20.
22

Table 17. Optical properties for aluminized beta cloth. 

	




Control 		  Environment

ISS batch,

MISSE-2 ram 0.34 0.37 0.03 6,000 ESH

 0.89 0.89 – 7.6 × 1021 O atoms/cm2 

ISS batch,

MISSE-2 wake 0.34 0.38 0.04 5,700 ESH

 0.89 0.89 – 1 × 1020 O atoms/cm2 

Boeing batch,

MISSE-3 ram 0.34 0.38 0.04 1,750 ESH

 0.89 0.89 – 1.2 × 1021 O atoms/cm2

Lockheed batch,

MISSE-3 ram 0.35 0.36 0.01 1,750 ESH

 0.90 0.89 –0.01 1.2 × 1021 O atoms/cm2

Lockheed batch,

MISSE-4 wake 0.35 0.34 –0.01 790 ESH

 0.90 0.89 –0.01 1.9 × 1020 O atoms/cm2

ISS batch,

MISSE-5 nadir 0.34 0.37 0.03 525 ESH

 0.89 0.89 – 1.8 × 1020 O atoms/cm2

ISS batch,

MISSE-6 ram 0.36 0.41 0.05 2,600 ESH

 0.87 0.88 0.01 2 × 1021 O atoms/cm2

ISS batch,

MISSE-6 wake 0.36 0.42 0.06 1,950 ESH

 0.87 0.89 0.02 1.2 × 1020 O atoms/cm2

Table 18. Optical properties for plain beta cloth.

	




Control 		  Environment

With 966 adhesive 

to aluminum plate,

MISSE-2 ram

0.29 0.30 0.01 6,000 ESH

 0.91 0.90 –0.01 7.6 × 1021 O atoms/cm2

With black 

background, 

MISSE-2 wake

0.35 0.38 0.03 5,700 ESH

 0.89 0.89 – 1 × 1020 O atoms/cm2

Aluminized Kapton 

background,

MISSE-3 ram

0.29 0.31 0.02 1,750 ESH 

 0.89 0.89 – 1.2 × 1021 O atoms/cm2

0.0127-cm (5-mil) 



	


MISSE-3 wake

0.28–0.29 0.29 0.01 790 ESH

 – 0.89 – 1.9 × 1020 O atoms/cm2
23

Table 19. Optical properties for super or plus beta cloth.

	




Control 		  Environment

MISSE-2 ram 0.36 0.38 0.02 6,000 ESH

 0.90 0.89 –0.01 7.6 × 1021 O atoms/cm2

MISSE-2 wake 0.36 0.40 0.04 5,700 ESH

 0.90 0.89 –0.01 1 × 1020 O atoms/cm2

Kapton background,

MISSE-5 nadir 0.27 0.30 0.03 525 ESH

 0.89 0.89 – 1.8 × 1020 O atoms/cm2

Table 20. Optical properties for PFOA-free beta cloth, black background.

	




Control 		  Environment

MISSE-6 ram 0.35 0.37 0.02 2,600 ESH

 0.89 0.89 – 2 × 1021 O atoms/cm2

MISSE-6 wake 0.36 0.39 0.03 1,950 ESH

 0.89 0.89 – 1.2 × 1020 O atoms/cm2

6.2 Hook and Loop Tape Fastener

 Aplix® hook and loop tape fastener samples (fig. 10) were flown on MISSE-2 and MISSE-3. 

For the ram-facing MISSE-2 samples, AO heavily eroded the polymeric hooks and loops into only 

nubs. The samples on the wake side of MISSE-3 indicated that fastener adhesion was still present 

after 1 × 1020 atoms/cm2. 

(a) (b)

Unexposed Exposed

Unexposed

Exposed

Figure 10. Aplix tape fastener samples from MISSE-2 ram side, showing UV 

darkening and nubs: (a) Hook and (b) loop. 
24

6.3 Thread

 One of the lessons from LDEF was the importance of thread selection for MLI blankets. 

DacronTM thread used on a heat pipe experiment was completely eroded away during the 5.8-year 

exposure.27 Aramid (Kevlar®) thread is occasionally used for short-duration exposures or where 

the blanket should be protected from AO, but most of the ISS MLI blankets use either fiberglass 

thread coated with polytetrafluoroethylene (PTFE) or stainless steel coated with PTFE. Triton 

Systems developed their Triton oxygen resistant (TOR) material into both cloth and thread for 

flight on MISSE-1 and MISSE-3 ram-facing sides. The sample in figure 11 was flown on MISSE-1 

with Kapton film behind it. The Kapton indicated some AO erosion where the sewing needle 

had pierced the fabric; otherwise, this sample was in very good condition for an AO exposure of 

9 × 1021 atoms/cm2. 

Figure 11. Triton TOR cloth and thread, MISSE-1 ram. 

Octagon is where sample was exposed to space.
25

 The 2-G1 sample from MISSE-2 was made up of old and new beta cloth, some with the aluminum light block layer or the Teflon removed, sewn with reinforced Kevlar thread (fig. 12). This 

thread was still intact after an AO exposure of 7.6 × 1021 atoms/cm2.

Figure 12. Samples of beta cloth sewn with reinforced thread.
26

7. POLYMERS

 Teflon metallized with either aluminum or silver and Inconel is a common thermal control 

material on the ISS (tables 21 and 22). The usual thickness of the Teflon layer is 0.0254 cm (10 mil), 

though 0.00254 cm (1 mil), 0.00508 cm (2 mil), and 0.0127 cm (5 mil) samples have been flown on 

MISSE. In addition, some samples of silverized Teflon had a silicon oxide (SiOx) protective coating 

(table 23).

Table 21. Optical properties for aluminized Teflon.

	




Control 		  Environment

0.00508 cm (2 mil),

MISSE-6 ram

0.12 0.12 – 2,600 ESH

 0.65 0.65 – 2 × 1021 O atoms/cm2

0.00508 cm (2 mil),

MISSE-6 wake

0.12 0.12 – 1,950 ESH

 0.65 0.65 – 1.2 × 1020 O atoms/cm2
27

Table 22. Optical properties for silverized Teflon.

	




Control 		  Environment

0.00508 cm (2 mil),

MISSE-2 ram 0.07 0.07 – 6,000 ESH

 0.64 0.59 –0.05 7.6 × 1021 O atoms/cm2

0.0127 cm (5 mil),

MISSE-2 ram 0.08 0.07 –0.01 6,000 ESH

 0.78 0.77 –0.01 7.6 × 1021 O atoms/cm2

0.0254 cm (10 mil),

MISSE-2 ram 0.08 0.08 – 6,000 ESH

 0.85 0.85 – 7.6 × 1021 O atoms/cm2

0.00254 cm (1 mil),

MISSE-2 wake 0.06 0.07 0.01 5,700 ESH

 0.52 0.53 0.01 1 × 1020 O atoms/cm2

0.00508 cm (2 mil),

MISSE-2 wake 0.07 0.07 – 5,700 ESH

 0.64 0.65 0.01 1 × 1020 O atoms/cm2

0.0127 cm (5 mil),

MISSE-2 wake 0.08 0.07 –0.01 5,700 ESH

 0.78 0.79 0.01 1 × 1020 O atoms/cm2

0.0127 cm (5 mil),

MISSE-5 nadir 0.08 0.07 –0.01 525 ESH

 0.78 0.78 – 1.8 × 1020 O atoms/cm2

0.0254 cm (10 mil)

with 966 adhesive

MISSE-6 ram

0.07 0.09 0.02 2,600 ESH

 0.85 0.85 – 2 x 1021 O atoms/cm2

0.0254 cm (10 mil),

MISSE-7B ram 0.09 0.10 0.01 2,400 ESH 

 0.85 0.85 – 4.2 × 1021 O atoms/cm2

0.0254 cm (10 mil),

MISSE-7B wake 0.09 0.09 – 2,000 ESH 

 0.85 0.85 – 2.9 × 1020 O atoms/cm2

0.0254 cm (10 mil)

with 966 adhesive,

MISSE-7B ram

0.08 0.09 0.01 2,400 ESH 

 0.85 0.86 0.01 4.2 × 1021 O atoms/cm2

0.0254 cm (10 mil)

with 966 adhesive,

MISSE-7B wake

0.08 0.09 0.01 2,000 ESH 

 0.85 0.86 0.01 2.9 × 1020 O atoms/cm2

Table 23. Optical properties for silverized Teflon with SiOx coating. 

	




Control 		  Environment 

0.014 cm (5.5 mil),

MISSE-1 ram

0.08 0.08 – 7,000 ESH

 0.80 0.80 – 9 × 1021 O atoms/cm2

0.014 cm (5.5 mil),

MISSE-2 wake

0.08 0.08 – 5,700 ESH

 0.80 0.80 – 1 × 1020 O atoms/cm2
28

 Indium tin oxide (ITO) coating on Kapton has been used on the ISS for both thermal control 

and static dissipation. Two different thickness of ITO were flown on MISSE-7, with the thicker ITO 

maintaining electrical properties of 1,500 to 1,600 Ω/. The thinner, higher resistance ITO was still 

static dissipative but increased from 20,000 Ω/to 2 to 3 × 106 Ω/. The change in properties for a 

17-month exposure (table 24) indicates this material should be used for short duration only. Also, 

care should be taken in handling ITO-coated materials, as they are easily damaged.

Table 24. Optical properties for ITO on Kapton.

	




Control 		  Environment

1500 Ω/

MISSE-7B wake

0.40 0.40 – 2,000 ESH 

 0.79 0.79 – 2.9 × 1020 O atoms/cm2

20,000 Ω/

MISSE-7B wake

0.41 0.41 – 2,000 ESH 

 0.80 0.80 – 2.9 × 1020 O atoms/cm2
29

8. OPTICAL MATERIALS

 Magnesium fluoride windows were flown as optical witness samples for measuring contamination and also to protect certain samples, such as solar sail materials and the candidate sunshade 

material for the James Webb Space Telescope. This allowed UV radiation to reach the thin polymer 

films without their being exposed to AO. The longer exposure of the windows on MISSE-2 indicated 

an AO effect on their transmission capabilities, rather than contamination of the window material. 

Figure 13 compares two flight magnesium fluoride windows from MISSE with two from POSA-I 

with corresponding control samples. ESCA showed that the MISSE windows had ≈50 Å of SiOx, as 

opposed to about 500 Å of SiOx on the POSA windows. 

100

90

80

70

60

50

40

30

20

10

0

120 140 160 180

Wavelength (nm)

200 220 240 260

MISSE Control

MISSE-2 Ram

Tray E7

Misse-2 Ram 

Tray E8

POSA Control

POSA S1A

POSA S2D

Transmission (%)

Figure 13. Comparison of MISSE versus POSA for vacuum UV transmission 

of magnesium fluoride.

 Samples of Russian quartz similar to the Earth observation windows on the Zvezda Service 

Module were flown on both sides of MISSE-6B. Figure 14 shows a slight decrease in transmission in 

the UV wavelengths. These samples had no visible change in appearance. 
30

100

90

80

70

60

50

40

30

20

10

0

200 300 400 500

Wavelength (nm)

600 700 800

Transmission (%)

Ram-Flight

Wake-Facing

Control

Figure 14. Transmission of Russian quartz samples flown on MISSE-6B.

 Another set of samples flown on MISSE-6B was Hyzod® polycarbonate, used as scratch 

panes or debris panes protecting ISS windows. The polycarbonate has a protective coating, otherwise 

it would be heavily eroded by AO. Some UV darkening was observed (fig. 15), and the transmission 

measurements are presented in figure 16.

Figure 15. Hyzod polycarbonate flown on MISSE-6B wake side.
31

100

90

80

70

60

50

40

30

20

10

0

350 400 450 500

Wavelength (nm)

550 600 650 700 750 800

Transmission (%)

Preflight

Postflight Ram Facing

Postflight Wake Facing

Figure 16. Visible wavelength transmission for Hyzod polycarbonate.
32

9. PART MARKING

9.1 Metalphoto®/Photofoil Labels

 Metalphoto or Photofoil anodized aluminum foil labels have been produced for the ISS by 

the Johnson Space Center Decal Design and Production Facility. The early labels used oxalic acid 

anodize with a NiAc seal similar to the SAA process described in section 4.3; the seals darkened in 

a similar way when exposed to UV radiation. Figure 17 shows the striking visual difference between 

the NiAc-sealed labels and the nickel-free labels on the S1 segment.

Figure 17. ISS S1 truss with (A) NiAc-sealed labels, which darkened, and (B) nickelfree labels, which were stable. 

 Metalphoto/Photofoil samples were flown on the MISSE-1 ram, the MISSE-2 wake, the 

MISSE-3 wake, the MISSE-4 ram, and the MISSE-7B ram and wake. Those samples containing 

nickel darkened considerably (fig. 18), with an average increase of 0.20 in α.
33

Figure 18. Metalphoto/Photofoil from MISSE-1 wake-facing side. White 

circles are where washers protected the surface from UV radiation. 

9.2 Ink Stamp Labels

 Ink stamp labels with an overcoat of clear Nusil CV-1144 silicone proved to be very durable 

on MISSE-1 ram and MISSE-3 ram (fig.19). 

Figure 19. Ink stamp with clear overcoat from MISSE-1 ram-facing side.
34

10. DISCUSSION AND CONCLUSIONS

The information presented here was gathered to support life extension and sustaining engineering for the ISS. The specific conditions on another spacecraft must be considered when choosing materials; i.e., what works for low Earth orbit conditions may not work in a geosynchronous, 

Lagrangian, or a lunar environment. Materials that have been shown to darken in UV may not be 

suitable for long-duration missions. Some margin should be included in a design for unexpected degradation or contamination events. The MISSE experiments had low or localized contamination that 

did not significantly affect the results of space environmental effects. Sensible contamination control procedures should be enforced to minimize the impact of contamination on spacecraft thermal 

performance.
35

REFERENCES 

 1. Finckenor, M.M.: “MISSE Materials Results for Application in the Vision for Space Exploration,” Paper presented at National Space & Missile Materials Symposium, Orlando, FL, 

June 26–30, 2006.

 2. Zwiener, J.M.; Alvis, A.H.; Jones, S.D.; and Finckenor, M.M.: “MSFC Analysis of Thermal 

Control Materials on MISSE,” Paper presented at National Space & Missile Materials Symposium, Orlando, FL, June 26–30, 2006.

 3. Finckenor, M.M.; and Pippin, G.: “Results from Optical Coatings Flown on MISSE-2 and 

other Flight Experiments,” Paper presented at National Space & Missile Materials Symposium, 

Orlando, FL, June 26–30, 2006.

 4. O’Rourke, M.J.; and Golden, J.L.: “International Space Station Vehicle Materials: Analysis of 

Results from MISSE 1 & 2,” Paper presented at National Space & Missile Materials Symposium, 

Keystone, CO, June 25–29, 2007.

 5. deGroh, K.K.; Finckenor, M.M.; Minton, T.; et al.: “Post-Flight Analysis of Selected Fluorocarbon and Other Thin Film Polymer Specimens Flown on MISSE-5,” Paper presented at National 

Space & Missile Materials Symposium, Keystone, CO, June 25–29, 2007.

 6. Finckenor, M.M.; Zwiener, J.M.; and Pippin, G.: “Thermal Control Materials on MISSE-5 with 

Comparison to Earlier Flight Data,” Paper presented at National Space & Missile Materials 

Symposium, Keystone, CO, June 25–29, 2007.

 7. Kenny, M.; McNulty, R.; and Finckenor, M.M.: “Analysis of Thermal Control Coatings on 

MISSE for Aerospace Applications,” Paper presented at National Space & Missile Materials 

Symposium, Keystone, CO, June 25–29, 2007.

 8. Finckenor, M.M.; Golden, J.L.; O’Rourke, M.J.: “Analysis of International Space Station 

Materials on MISSE-3 and MISSE-4,” Paper presented at National Space & Missile Materials 

Symposium, Henderson, NV, June 23–27, 2008.

 9. Kenny, M.; McNulty, R.; and Finckenor, M.M.: “Further Analysis of Thermal Control Coatings 

on MISSE for Aerospace Applications,” Paper presented at National Space & Missile Materials 

Symposium, Henderson, NV, June 22–25, 2009.

10. Golden, J.L.; O’Rourke, M.J.; and Finckenor, M.M.: “Analysis of Materials Returned 

from the Materials International Space Station Experiment (MISSE): MISSE-1, 2, 3, & 4,” 

Paper presented at National Space & Missile Materials Symposium, Henderson, NV, 

June 22–25, 2009.
36

11. Finckenor, M.M: “Further Analysis of MISSE Polymeric Materials at MSFC,” Paper presented 

at National Space & Missile Materials Symposium, Henderson, NV, June 22–25, 2009.

12. Finckenor, M.M.; Golden, J.L.; Kravchenko, M.; and O’Rourke, M.J.: “Analysis of International 

Space Station Vehicle Materials on MISSE-6,” Paper presented at National Space & Missile 

Materials Symposium, Scottsdale, AZ, June 29–July 2, 2010.

13. Finckenor, M.M.; Zwiener, J.M.; Alvis, A.; et al.: “Thermal Control Materials on MISSE-6 with 

Comparison to Earlier Flight Data,” Paper presented at National Space & Missile Materials 

Symposium, Scottsdale, AZ, June 29–July 2, 2010.

14. Finckenor, M.M.; Golden, J.L.; Kravchenko, M.; and O’Rourke, M.J.: “Results of International 

Space Station Vehicle Materials Exposed on MISSE-7B,” Paper presented at National Space & 

Missile Materials Symposium, Tampa, FL, June 25–29, 2012.

15. de Groh, K.K.; Banks, B.A.; McCarthy, C.E.; et al.: “MISSE PEACE Polymers Atomic Oxygen 

Erosion Results,” NASA/TM—2006–214482, Glenn Research Center, Cleveland, OH, November 2006.

16. Pippin, G.: “Summary Status of MISSE-1 and MISSE-2 Experiments and Details of Estimated 

Environmental Exposures for MISSE-1 and MISSE-2,” Paper presented at AFRL-ML-WPTR-2006-4237, July 2006.

17. Finckenor, M.M.; Pippin, G.; and Kinard, W.H.: “Estimated Environmental Exposures for 

MISSE-3 and MISSE-4,” Paper presented at National Space & Missile Material Symposium, 

Henderson, NV, June 2008.

18. deGroh, K.K.; Finckenor, M.M.; Minton, T.; et al.: “Post-Flight Analysis of Selected Fluorocarbon and Other Thin Film Polymer Specimens Flown on MISSE-5,” Paper presented at National 

Space & Missile Materials Symposium, Keystone, CO, June 25–29, 2007.

19. deGroh, K.K.; Banks, B.A.; Guo, A.; et al.: “MISSE 6 Polymers Atomic Oxygen Erosion Data,” 

Paper presented at National Space & Missile Materials Symposium, Scottsdale, AZ, June 28– 

July 1, 2010.

20. MIL-DTL-5541F, Military Specification: Chemical Conversion Coatings on Aluminum and 

Aluminum Alloys, 12 pp., July 11, 2006.

21. MIL-A-8625F, Military Specification: Anodic Coatings for Aluminum and Aluminum Alloys, 

20 pp., September 10, 1993.

22. Golden, J.L.: “Anodized Aluminum on LDEF: A Current Status of Measurements on Chromic 

Acid Anodized Aluminum,” in Proc. LDEF Materials Workshop, NASA CP-3162, November 

1991.
37

23. Finckenor, M.M.; Kamenetzky, R.; and Vaughn, J.A.: “Further Investigations of the Passive 

Optical Sample Assembly (POSA) – I Flight Experiment,” Paper AIAA-2001-0098 presented at 

39th AIAA Aerospace Sciences Meeting, Reno, NV, January 8–11, 2001.

24. Kamenetzky, R.R.; Finckenor, M.M.; and Vaughn, J.A.: “Space Environmental Effects on Colored Marker Coatings and Anodizes,” Paper presented at 44th International Society for the 

Advancement of Material and Process Engineering Symposium, Long Beach, CA, May 1999.

25. Zwiener, J.M.; Kamenetzky, R.R.; Vaughn, J.A.; and Finckenor, M.M.: “The Passive Optical 

Sample Assembly (POSA) - I Experiment: First Flight Results and Conclusions,” Paper AIAA 

99-0104 presented at 37th AIAA Aerospace Sciences Meeting, Reno, NV, January 11–14, 1999.

26. Koontz, S.L.; Jacobs, S.; and Le, J.: “Beta Cloth Durability Assessment for Space Station Freedom (SSF) Multi-Layer Insulation (MLI) Blanket Covers,” NASA TM-104748, Johnson Space 

Center, Houston, TX, March 1993.

27. Linton, R.; Whitaker, A.; and Finckenor, M.: “Space Environment Durability of Beta Cloth in 

LDEF Thermal Blankets,” in Proc. LDEF Materials Results for Spacecraft Applications Conference, NASA CP-3257, NASA Marshall Space Center, Huntsville, AL, October 1992.
38

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Analysis of International Space Station Vehicle Materials 

Exposed on Materials International Space Station 

Experiment From 2001 to 2011

M.M. Finckenor, J.L. Golden,* and M. Kravchenko*

George C. Marshall Space Flight Center

Huntsville, AL 35812

National Aeronautics and Space Administration

Washington, DC 20546–0001

Unclassified-Unlimited

Subject Category 27

Availability: NASA STI Information Desk (757–864–9658)

Prepared by the Materials & Processes Laboratory, Engineering Directorate

*The Boeing Company, Houston, Texas

M–1374

Technical Publication

NASA/TP—2013–217498

space environment, space station, materials, atomic oxygen, ultraviolet radiation, flight hardware, 

low Earth orbit, optical properties

01–12–2013

UU 52

NASA

UUU

Since August 2001, the Materials on International Space Station Experiment (MISSE) has provided data 

on a variety of materials and spacecraft components, including samples chosen to provide sustaining 

engineering and life extension data for the International Space Station vehicle itself. This Technical Publication is by no means a complete set of MISSE data but does provide changes in solar absorptance, infrared emittance, and visual appearance due to atomic oxygen, ultraviolet radiation, and thermal cycling in 

vacuum. Conversion coatings, anodizes, thermal control coatings with organic and inorganic binders, 

multilayer insulation components, optical materials, and part markings are discussed.

STI Help Desk at email: help@sti.nasa.gov

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